COMPOSITE MATERIAL STRUCTURE FOR AIRCRAFT FUSELAGE AND PROCESS FOR MANUFACTURING IT

摘要

The present invention provides a closed composite materialstructure for aircraft fuselage shaped on a male jig from whichit can be separated in a certain direction, said structurecomprising a single outer panel and a plurality of innerlongitudinal stiffeners integrated in said panel, such that theexpansion coefficient of the male jig is greater than theexpansion coefficient of the composite material of thestructure, thus being able to remove the already manufacturedstructure, formed by the panel and the integrated innerstiffeners, in a single operation. The present invention furtherprovides a process for manufacturing such a closed structure.